Power Architectures and Power Conditioning Unit for Very Small Satellites

Oprea, Sergiu; Radoi, C.; Florescu, Adriana; Savu, Andrei; Lita, Adrian-Ioan

doi:10.1007/978-3-319-49875-1_17

Cited by 5 publications

(3 citation statements)

References 9 publications

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“…Most of the typical voltages required for the CubeSat onboard equipment are in the range of 3 to 6 volts. The EPS is highly segmented, each segment of which is usually supplied through a dedicated buck or boost dc-dc converter and necessary switching gear [53]. These subsections are well fragmented to overcome the noises and ripple creeping since the nature of the loads can be RF, analog, or digital [54].…”

Section: A Dc-dc Convertersmentioning

confidence: 99%

A Comprehensive Review on Small Satellite Microgrids

Yaqoob

Lashab

Vasquez

et al. 2022

IEEE Trans. Power Electron.

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The Small Satellite (SmallSat) industry has recorded incredible growth recently. Within this class, among Mini-, Micro-, and Nanosatellites, the Cube Satellite (CubeSat) is primed for an explosion of growth. These satellites are fascinating for remote sensing, earth observation, and scientific applications. Remarkable attention from the space operators makes it valuable because of its low cost, cubic shape, less manufacturing time, lightweight, and modular structure. Among the various subsystems comprising the SmallSat, the Electrical Power System (EPS) is the most crucial one because unreliable power supply to the rest is most of the time detrimental to the mission. The EPS is formed by electrical sources, storage units, and loads, all interconnected via different power converters, the operation of which must be closely orchestrated to accomplish efficient use of photovoltaic power, optimal battery management, and resilient power delivery. At the same time, the EPS design must address a series of challenges such as size restrictions, high power density, harsh space environments (e.g., atomic oxygen, radiation, and extreme temperatures) which significantly impact the EPS electrical and electronic equipment. In terms of power systems, a SmallSat EPS can be considered a space microgrid owing coordination and control of distributed generation (DG), storage and loads in a small-scale electrical network. From this point of view, this paper reviews and explores SmallSat microgrid's research developments, energy transfer and architectures, converter topologies, latest technologies, main challenges, and some potential solutions which will enable building a more robust, resilient, and efficient EPS. The research gaps and future developments are underlined before the paper is concluded.

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Section: A Dc-dc Convertersmentioning

confidence: 99%

A Comprehensive Review on Small Satellite Microgrids

Yaqoob

Lashab

Vasquez

et al. 2022

IEEE Trans. Power Electron.

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“…The present strategy to estimate the maximum power point of a solar panel (or solar array) has been developed to extract energy from the panel to a power bus at a lower, bigger, or equal voltages and therefore covers a general arrangement used in autonomous systems, such as telecommunications and Earth observation satellites [6], and even smaller spacecraft platforms [7]. The power bus fed by the solar panel does not need to be precisely regulated, the only requirement for it is having a voltage that changes slowly with time (as in battery bus for example) in order to not interfere with the MPPT tracking circuitry, and thus this strategy is general and may be readily used in non-regulated buses as well as regulated ones.…”

Section: Working Principle Of the Proposed Maximum Power Point Estimatormentioning

confidence: 99%

A PWM multiplier for maximum power point estimation of a solar panel

Carrasco

Quirós

Alavés

et al. 2018

IEICE Electron. Express

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A simple analog multiplier for the estimation of the power yield of a solar panel may be realized with a pulse width modulator working as analog multiplier circuit of the current yield and the duty cycle of the converter used to condition the panel. Though the output of the pulse width modulator multiplication is not exactly proportional to the output power of the solar panel, its maximum follows the maximum of the power curve of the panel. This multiplier allows a complete analog implementation of the maximum power point tracker of the panel keeping, at the same time, the simplicity needed in robust electronic systems. This paper presents the working principle of the maximum power point estimator for three different power conditioners of the solar panel: a step-down, a step-up and a SEPIC.

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“…Block diagrams of these architectures are included in Figure 1, the block names are given in Table 1. A short description of each architecture is provided as follows, and a comparison is included in Table 2; for more detailed information, see Section 17.2.3 of [3]. BCDET: In this implementation, the solar array and the battery are both connected to the bus; therefore, the solar array power output is dependent on the state of charge (SOC) of the battery.…”

Section: Introductionmentioning

confidence: 99%

A Lean Satellite Electrical Power System with Direct Energy Transfer and Bus Voltage Regulation Based on a Bi-Directional Buck Converter

2020

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The lean satellite approach requires aggressive measures for cutting development time and resource utilization; therefore, the power system should be simple, with a low part count, high reliability, and good electrical performance. The fully-regulated bus direct energy transfer (FRDET) architecture is considered the most common solution for big satellites; however, it is rarely used in lean satellite designs because of its complexity and the lack of commercial off-the-shelf solutions. Based on this, a new implementation of the FRDET architecture was proposed, prototyped, and evaluated. The system was based on a bidirectional converter that charges and discharges the battery while maintaining the bus voltage regulation. The system was evaluated by comparing it with the prevailing architectures in the field, in terms of efficiency and average harvested solar power per orbit. The proposed system was superior in both aspects which made it more suitable for its application in lean satellite designs.

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Power Architectures and Power Conditioning Unit for Very Small Satellites

Cited by 5 publications

References 9 publications

A Comprehensive Review on Small Satellite Microgrids

A Comprehensive Review on Small Satellite Microgrids

A PWM multiplier for maximum power point estimation of a solar panel

A Lean Satellite Electrical Power System with Direct Energy Transfer and Bus Voltage Regulation Based on a Bi-Directional Buck Converter

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